Modular unmanned aerial vehicle with adjustable center of gravity

Abstract

An aerial vehicle system including a vertical takeoff and landing apparatus, a wing assembly removably coupled to the vertical takeoff and landing apparatus, and a rotor guard interchangeable with the wing assembly and removably coupleable to the vertical takeoff and landing apparatus. The vertical takeoff and landing apparatus can include a frame, a control module carried by the frame, and a plurality of thrust assemblies carried by the frame.

What is claimed is: 
     
         1 . An aerial vehicle system, comprising:
 a vertical takeoff and landing apparatus, including:
 a frame; 
 a control module carried by the frame; and 
 a plurality of thrust assemblies carried by the frame; and 
   a wing assembly removably coupled to the vertical takeoff and landing apparatus.   
     
     
         2 . The aerial vehicle system of  claim 1 , wherein at least one of the thrust assemblies is rotatable between a first position to provide vertical thrust and a second position to provide horizontal thrust. 
     
     
         3 . The aerial vehicle system of  claim 2 , further comprising a positioning mechanism coupled to the at least one of the thrust assemblies and operable to rotate the at least one of the thrust assemblies between the first and second positions. 
     
     
         4 . The aerial vehicle system of  claim 1 , wherein selected ones of the plurality of thrust assemblies each comprise a rotor assembly having a motor and at least one rotor. 
     
     
         5 . The aerial vehicle system of  claim 4 , further comprising a rotor guard interchangeable with the wing assembly and removably coupleable to the vertical takeoff and landing apparatus. 
     
     
         6 . The aerial vehicle system of  claim 1 , wherein the location of the wing assembly is adjustable fore and aft with respect to the vertical takeoff and landing apparatus. 
     
     
         7 . The aerial vehicle system of  claim 1 , further comprising one or more receptacles positioned on one of the wing assembly and the vertical takeoff and landing apparatus and one or more mating connectors positioned on the other of the wing assembly and the vertical takeoff and landing apparatus. 
     
     
         8 . The aerial vehicle system of  claim 7 , wherein the connectors are attachable to the receptacles and securable thereto at multiple longitudinal positions. 
     
     
         9 . The aerial vehicle system of  claim 1 , wherein the wing assembly comprises a closed wing structure. 
     
     
         10 . An aerial vehicle system, comprising:
 a vertical takeoff and landing apparatus, including:
 a frame; 
 a control module carried by the frame; and 
 a plurality of thrust assemblies carried by the frame, wherein at least one of the thrust assemblies is rotatable between a first position to provide vertical thrust and a second position to provide horizontal thrust; 
   a wing assembly removably coupleable to the vertical takeoff and landing apparatus; and   a rotor guard interchangeable with the wing assembly and removably coupleable to the vertical takeoff and landing apparatus.   
     
     
         11 . The aerial vehicle system of  claim 10 , wherein the wing assembly comprises a closed wing structure. 
     
     
         12 . The aerial vehicle system of  claim 10 , further comprising a positioning mechanism coupled to the at least one of the thrust assemblies and operable to rotate the at least one of the thrust assemblies between the first and second positions. 
     
     
         13 . The aerial vehicle system of  claim 10 , wherein the location of at least one of the wing assembly and the rotor guard is adjustable fore and aft with respect to the vertical takeoff and landing apparatus. 
     
     
         14 . The aerial vehicle system of  claim 13 , further comprising a plurality of receptacles positioned on one of the wing assembly and the vertical takeoff and landing apparatus and a corresponding plurality of mating connectors positioned on the other of the wing assembly and the vertical takeoff and landing apparatus. 
     
     
         15 . The aerial vehicle system of  claim 14 , wherein the connectors are attachable to the receptacles and securable thereto at multiple longitudinal positions. 
     
     
         16 . The aerial vehicle system of  claim 10 , wherein selected ones of the plurality of thrust assemblies each comprise a rotor assembly having a motor and at least one rotor. 
     
     
         17 . A method for reconfiguring an aerial vehicle, the method comprising:
 positioning a wing assembly on a vertical takeoff and landing apparatus;   operating the vertical takeoff and landing apparatus with the wing assembly positioned thereon;   removing the wing assembly from the vertical takeoff and landing apparatus; and   operating the vertical takeoff and landing apparatus without the wing assembly.   
     
     
         18 . The method of  claim 17 , further comprising moving the wing assembly longitudinally fore and aft of the vertical takeoff and landing apparatus and securing the wing assembly on the vertical takeoff and landing apparatus at a first longitudinal location. 
     
     
         19 . The method of  claim 17 , further comprising positioning a rotor guard on the vertical takeoff and landing apparatus and securing the rotor guard thereon at a second longitudinal location. 
     
     
         20 . The method of  claim 17 , wherein the vertical takeoff and landing apparatus includes a plurality of thrust assemblies, the method further comprising rotating at least one of the thrust assemblies between a first position to provide vertical thrust and a second position to provide horizontal thrust.